def my_func(M,P,T,aoa,span,tip_chord):
chord[1] = tip_chord
mesh_utils.write_wing_file(M,P,T,chord,span,n_sections,n_naca_pts)
NACA.create_wing('current_wing','output')
run_apame(aoa)
fid = open('output_polar.dat','r')
nb_lines=0
while fid.readline():
nb_lines+=1
if nb_lines==0:
raise TypeError("Empty file")
fid.close()
fid = open('output_polar.dat','r')
# revenir au debut
alpha=numpy.zeros(nb_lines)
cx=numpy.zeros(nb_lines)
cz=numpy.zeros(nb_lines)
for i in xrange(nb_lines):
tmp=fid.readline()
tmp=tmp.split()
alpha[i]=float(tmp[0])
cx[i]=float(tmp[2])
cz[i]=float(tmp[1])
fid.close()
ind = cx.argmin()
Cf = 0.0583/Re**0.2
Sw = (chord[0]+chord[1])*span/2.
Cd_friction = Sw/Sref*Cf
return min(cx)+Cd_friction,cz[ind]
def my_func(M, P, T, span, tip_chord):
chord[1] = tip_chord
mesh_utils.write_wing_file(M, P, T, chord, span, n_sections, n_naca_pts)
NACA.create_wing("current_wing", "output")
run_apame()
fid = open("output_polar.dat", "r")
nb_lines = 0
while fid.readline():
nb_lines += 1
if nb_lines == 0:
raise TypeError("Empty file")
fid.close()
fid = open("output_polar.dat", "r")
# revenir au debut
alpha = numpy.zeros(nb_lines)
cx = numpy.zeros(nb_lines)
cz = numpy.zeros(nb_lines)
finesse = numpy.zeros(nb_lines)
Cf = 0.0583 / Re ** 0.2
Sw = (chord[0] + chord[1]) * span / 2.0
Cd_friction = Sw / Sref * Cf
for i in xrange(nb_lines):
tmp = fid.readline()
tmp = tmp.split()
alpha[i] = float(tmp[0])
cx[i] = float(tmp[2]) + Cd_friction
cz[i] = float(tmp[1])
finesse[i] = cz[i] / cx[i]
fid.close()
return max(finesse)
def my_func(X):
chord=[1.,1.]
M=X[0:2]
P=X[2:4]
T=X[4:6]
alpha=X[6]
span=X[7]
chord[1]=X[8]
n_sections=31
n_naca_pts=50
Sref=10.
Re=5.e5
mesh_utils.write_wing_file(M,P,T,chord,span,n_sections,n_naca_pts)
NACA.create_wing('current_wing','output')
run_apame(alpha)
fid = open('output_polar.dat','r')
nb_lines=0
while fid.readline():
nb_lines+=1
if nb_lines==0:
raise TypeError("Empty file")
fid.close()
fid = open('output_polar.dat','r')
# revenir au debut
alpha=numpy.zeros(nb_lines)
cx=numpy.zeros(nb_lines)
cz=numpy.zeros(nb_lines)
for i in xrange(nb_lines):
tmp=fid.readline()
tmp=tmp.split()
alpha[i]=float(tmp[0])
cx[i]=float(tmp[2])
cz[i]=float(tmp[1])
fid.close()
#f = interpolate.interp1d(numpy.array(cz), numpy.array(cx), kind='cubic')
#print 'DRAG >>> ', min(cx)
#cx=f(0.5)
ind = cx.argmin()
Cf = 0.0583/Re**0.2
Sw = (chord[0]+chord[1])*span/2.
Cd_friction = Sw/Sref*Cf
print 'DRAG >>> ', cx+Cd_friction
cx_tab[k]=cx+Cd_friction
contrainte_tab[k]=0.5-cz
k=k+1
return cx+Cd_friction#,cz[ind]
beta=beta_list,
v=airspeed,
rho=rho,
P=Patm,
Mach=0.,
origin=[0.,0.,0.],
wingspan=10.,
ref_chord=1.,
Sref=Sref,
method=0,
farfield_dist=50.,
velorder=1)
if nb==8415:
nb_angles=11
M=[0.08,0.08]
P=[0.4,0.4]
T=[0.15,0.15]
elif nb==12:
nb_angles=21
M=[0.0,0.0]
P=[0.4,0.4]
T=[0.12,0.12]
mesh_utils.write_wing_file(M,P,T,chord,span,n_sections,n_naca_pts)
NACA.create_wing('current_wing','initial'+str(nb))
run_apame(nb_angles)
def create_mesh_linear_interp(filename,root,tip,span,n_sections,n_naca_points=150):
if n_sections%2 == 0:
raise ValueError("Merci de donner un nombre de sections impair")
if type(root) is not list:
raise TypeError("Le deuxieme argument doit etre une liste contenant M,P,T et Chord pour la section root.")
if type(tip) is not list:
raise TypeError("Le troisieme argument doit etre une liste contenant M,P,T et Chord pour la section tip.")
if type(filename) is not str:
raise TypeError("Le premier argument doit etre un string (nom du fichier de sortie).")
if len(root)!=4:
raise ValueError("Le deuxieme argument doit etre une liste contenant 4 valeurs (M,P,T,Chord).")
if len(tip)!=4:
raise ValueError("Le troisieme argument doit etre une liste contenant 4 valeurs (M,P,T,Chord).")
ind_root=(n_sections-1)//2
semi_span = span/2.
theta = numpy.linspace(0.,numpy.pi,n_sections)
y_list = -semi_span*numpy.cos(theta)
y_list[ind_root]=0. # souvent 10^-16
m_root,p_root,t_root,chord_root=root
m_tip,p_tip,t_tip,chord_tip=tip
Xu_tip,Xl_tip,Yu_tip,Yl_tip = NACA.create(m_tip,p_tip,t_tip,chord_tip,n_naca_points)
upper_tip = numpy.array([Xu_tip,Yu_tip]).T
lower_tip = numpy.array([Xl_tip,Yl_tip]).T
tip_section = numpy.concatenate((lower_tip[::-1],upper_tip[1:]))
Xu_root,Xl_root,Yu_root,Yl_root = NACA.create(m_root,p_root,t_root,chord_root,n_naca_points)
upper_root = numpy.array([Xu_root,Yu_root]).T
lower_root = numpy.array([Xl_root,Yl_root]).T
root_section = numpy.concatenate((lower_root[::-1],upper_root[1:]))
# build mesh
vtk_model = vtk.vtkStructuredGrid()
vtk_model.SetDimensions(2*n_naca_points-1,n_sections,1)
# build points
vtk_points = vtk.vtkPoints()
for i in xrange(n_sections):
r = numpy.abs(y_list[i])/semi_span
current_section = (1.-r)*root_section + r*tip_section
for j in xrange(2*n_naca_points-1):
vtk_points.InsertNextPoint(current_section[j,0],y_list[i],current_section[j,1])
# set points
vtk_model.SetPoints(vtk_points)
# convert to poly data
pdata_filter = vtk.vtkGeometryFilter()
if vtk.VTK_MAJOR_VERSION <= 5:
pdata_filter.SetInput(vtk_model)
else:
pdata_filter.SetInputData(vtk_model)
pdata_filter.Update()
poly_data = pdata_filter.GetOutput()
# compute normals
norms = vtk.vtkPolyDataNormals()
if vtk.VTK_MAJOR_VERSION <= 5:
norms.SetInput(poly_data)
else:
norms.SetInputData(poly_data)
norms.ComputePointNormalsOff()
norms.ComputeCellNormalsOn()
norms.ConsistencyOn()
norms.Update()
# clean poly data
clean_poly = vtk.vtkCleanPolyData()
clean_poly.ToleranceIsAbsoluteOn()
clean_poly.SetAbsoluteTolerance(1.e-6)
if vtk.VTK_MAJOR_VERSION <= 5:
clean_poly.SetInput(norms.GetOutput())
else:
clean_poly.SetInputData(norms.GetOutput())
clean_poly.Update()
# write output mesh
writer = vtk.vtkXMLPolyDataWriter()
if vtk.VTK_MAJOR_VERSION <= 5:
writer.SetInput(clean_poly.GetOutput())
else:
writer.SetInputData(clean_poly.GetOutput())
writer.SetFileName(filename+'.vtp')
writer.Write()
